JP2011522990A - Method for cleaning a fuel system of a gas turbine and the fuel system - Google Patents

Method for cleaning a fuel system of a gas turbine and the fuel system Download PDF

Info

Publication number
JP2011522990A
JP2011522990A JP2011512910A JP2011512910A JP2011522990A JP 2011522990 A JP2011522990 A JP 2011522990A JP 2011512910 A JP2011512910 A JP 2011512910A JP 2011512910 A JP2011512910 A JP 2011512910A JP 2011522990 A JP2011522990 A JP 2011522990A
Authority
JP
Japan
Prior art keywords
burner
injection point
injection
fuel
inlet pipe
Prior art date
Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
Granted
Application number
JP2011512910A
Other languages
Japanese (ja)
Other versions
JP5220190B2 (en
Inventor
ヴァーグナー、ウルリッヒ
バスマン、カルステン
ウヴェ ラウー、ホルスト
エルトレ、フォルカー
ニーンハウス、ミヒァエル
ラツォウスキ、ダミアン
ショイアー、ウヴェ
Current Assignee (The listed assignees may be inaccurate. Google has not performed a legal analysis and makes no representation or warranty as to the accuracy of the list.)
Siemens AG
Original Assignee
Siemens AG
Priority date (The priority date is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the date listed.)
Filing date
Publication date
Application filed by Siemens AG filed Critical Siemens AG
Publication of JP2011522990A publication Critical patent/JP2011522990A/en
Application granted granted Critical
Publication of JP5220190B2 publication Critical patent/JP5220190B2/en
Expired - Fee Related legal-status Critical Current
Anticipated expiration legal-status Critical

Links

Images

Classifications

    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
    • F02C—GAS-TURBINE PLANTS; AIR INTAKES FOR JET-PROPULSION PLANTS; CONTROLLING FUEL SUPPLY IN AIR-BREATHING JET-PROPULSION PLANTS
    • F02C7/00—Features, components parts, details or accessories, not provided for in, or of interest apart form groups F02C1/00 - F02C6/00; Air intakes for jet-propulsion plants
    • F02C7/22—Fuel supply systems
    • F02C7/232—Fuel valves; Draining valves or systems
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
    • F02C—GAS-TURBINE PLANTS; AIR INTAKES FOR JET-PROPULSION PLANTS; CONTROLLING FUEL SUPPLY IN AIR-BREATHING JET-PROPULSION PLANTS
    • F02C7/00—Features, components parts, details or accessories, not provided for in, or of interest apart form groups F02C1/00 - F02C6/00; Air intakes for jet-propulsion plants
    • F02C7/22—Fuel supply systems
    • F02C7/222—Fuel flow conduits, e.g. manifolds
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F23—COMBUSTION APPARATUS; COMBUSTION PROCESSES
    • F23K—FEEDING FUEL TO COMBUSTION APPARATUS
    • F23K5/00—Feeding or distributing other fuel to combustion apparatus
    • F23K5/02—Liquid fuel
    • F23K5/14—Details thereof
    • F23K5/18—Cleaning or purging devices, e.g. filters
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
    • F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
    • F01D25/00—Component parts, details, or accessories, not provided for in, or of interest apart from, other groups
    • F01D25/002—Cleaning of turbomachines
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
    • F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
    • F05D2260/00—Function
    • F05D2260/60—Fluid transfer
    • F05D2260/607—Preventing clogging or obstruction of flow paths by dirt, dust, or foreign particles
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F23—COMBUSTION APPARATUS; COMBUSTION PROCESSES
    • F23K—FEEDING FUEL TO COMBUSTION APPARATUS
    • F23K2300/00—Pretreatment and supply of liquid fuel
    • F23K2300/20—Supply line arrangements
    • F23K2300/203—Purging
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F23—COMBUSTION APPARATUS; COMBUSTION PROCESSES
    • F23N—REGULATING OR CONTROLLING COMBUSTION
    • F23N2227/00—Ignition or checking
    • F23N2227/04—Prepurge
    • Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
    • Y10—TECHNICAL SUBJECTS COVERED BY FORMER USPC
    • Y10T—TECHNICAL SUBJECTS COVERED BY FORMER US CLASSIFICATION
    • Y10T137/00—Fluid handling
    • Y10T137/0318—Processes
    • Y10T137/0402—Cleaning, repairing, or assembling
    • Y10T137/0419—Fluid cleaning or flushing
    • Y10T137/0424—Liquid cleaning or flushing

Landscapes

  • Engineering & Computer Science (AREA)
  • Chemical & Material Sciences (AREA)
  • Combustion & Propulsion (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Feeding And Controlling Fuel (AREA)
  • Nozzles For Spraying Of Liquid Fuel (AREA)

Abstract

ガスタービンにおけるバーナの燃料系統の部分域を洗浄する方法は、燃料を燃料源からバーナ（１０２）に導入するための入口配管（１００）の用意、該入口配管（１００）に媒体をそれぞれ注入するためのバーナ近隣注入点（１０８）およびバーナ遠隔注入点（１１０）の用意、バーナ近隣注入点（１０８）を介しての媒体の注入、入口配管（１００）におけるバーナ近隣注入点（１０８）とバーナ（１０２）との間に存在する燃料のバーナ（１０２）を介しての排出、バーナ遠隔注入点（１１０）を介しての媒体の注入および入口配管（１００）におけるバーナ遠隔注入点（１１０）とバーナ近隣注入点（１０８）との間に存在する燃料のバーナ近隣注入点（１０８）を介しての排出の過程を含んでいる。
【選択図】図１A method for cleaning a partial area of a fuel system of a burner in a gas turbine includes preparing an inlet pipe (100) for introducing fuel from a fuel source to the burner (102), and injecting a medium into the inlet pipe (100). A burner adjacent injection point (108) and a burner remote injection point (110) for injection, medium injection through the burner adjacent injection point (108), burner adjacent injection point (108) and burner in the inlet pipe (100) Discharge of the fuel existing between (102) through the burner (102), injection of the medium through the burner remote injection point (110) and the burner remote injection point (110) in the inlet pipe (100) This includes the process of discharging the fuel existing between the burner adjacent injection point (108) through the burner adjacent injection point (108).
[Selection] Figure 1

Description

本発明は、燃料を燃料源からバーナに導入するための入口配管の用意とこの入口配管に存在する燃料の排出ないし洗浄の過程とを含むガスタービンにおけるバーナの燃料系統の部分域を洗浄する方法に関する。本発明はまた、燃料を燃料源からバーナに導入するための入口配管と媒体を入口配管に注入するための注入点とを備えたガスタービンにおけるバーナの燃料系統に関する。   The present invention relates to a method for cleaning a partial area of a burner fuel system in a gas turbine comprising the provision of an inlet pipe for introducing fuel from a fuel source into the burner and the process of discharging or cleaning the fuel present in the inlet pipe. About. The invention also relates to a burner fuel system in a gas turbine comprising an inlet line for introducing fuel from a fuel source to the burner and an injection point for injecting medium into the inlet line.

燃料油運転式ガスタービンにおいては、運転後にバーナおよびそこに接続された入口配管から、燃料油ないし液体燃料のその高温表面における燃料のコークス化を防止するために除去されねばならない。そのコークス化は配管およびバーナを閉塞させ使用不能にしてしまう。   In a fuel oil-operated gas turbine, after operation, it must be removed from the burner and inlet piping connected thereto to prevent coking of the fuel or liquid fuel at its hot surface. The coking will block the piping and burner, making it unusable.

ガスタービンにおけるバーナおよび供給配管が、その配管ないしバーナから燃料油を除去するために、洗浄される方法が特許文献１で知られている。燃料油管の公知の排液は２回の過程で行われる。まずバーナが洗浄される。そのために水が（燃料油／水・乳濁液運転のためにもともと存在する）ＮＯｘ対策用の水供給装置の水管を通してバーナ近くのＴ形管部材を介してバーナ近くの燃料油管に、およびそれに続いて燃焼器に圧送される。これによって、バーナ、および、バーナ近隣Ｔ形管部材とバーナとの間の管部材から燃料油が排液される。そして第２過程においてＮＯｘ水供給装置の水がバーナ近隣Ｔ形管部材を介して燃料油管に圧送される。水はそこから燃料油管内に存在する燃料油を燃料油供給装置（燃料油・水注入ユニット）の方向に押し出し、そこから多機能弁の開いた弁を介して排液装置に運ばれる。かかる洗浄方法およびその燃料系統の場合、所定の運転条件において燃料油管に残滓が残存してしまう。   Patent Document 1 discloses a method in which a burner and a supply pipe in a gas turbine are washed to remove fuel oil from the pipe or burner. The known drainage of the fuel oil pipe takes place in two steps. First, the burner is cleaned. To that end, water flows into the fuel oil pipe near the burner through the T-shaped pipe member near the burner through the water pipe of the water supply device for NOx countermeasures (which originally exists for fuel oil / water / emulsion operation), and to it. Subsequently, it is pumped to the combustor. As a result, the fuel oil is discharged from the burner and the tube member between the burner adjacent T-shaped tube member and the burner. In the second process, the water in the NOx water supply device is pumped to the fuel oil pipe through the burner neighboring T-shaped pipe member. From there, the water pushes the fuel oil present in the fuel oil pipe in the direction of the fuel oil supply device (fuel oil / water injection unit), and is carried from there to the drainage device through the valve that is opened with the multi-function valve. In the case of such a cleaning method and its fuel system, residue remains in the fuel oil pipe under predetermined operating conditions.

欧州特許出願公開第０９３９２２０号明細書European Patent Application No. 0939220

本発明の課題は、上述の欠点が解消され同時に簡単で安価な様式の洗浄が可能であるガスタービンにおけるバーナの燃料系統の部分域を洗浄する方法とその燃料系統を提供することにある。   An object of the present invention is to provide a method and a fuel system for cleaning a partial area of a burner fuel system in a gas turbine which eliminates the above-mentioned drawbacks and at the same time allows a simple and inexpensive cleaning.

この課題は本発明に基づいて、請求項１に記載のガスタービンにおけるバーナの燃料系統の部分域を洗浄する方法および請求項５に記載のガスタービンにおけるバーナの燃料系統によって解決される。本発明の有利な実施態様は従属請求項に記載されている。   This object is achieved according to the invention by a method for cleaning a partial region of a burner fuel system in a gas turbine according to claim 1 and a burner fuel system in a gas turbine according to claim 5. Advantageous embodiments of the invention are described in the dependent claims.

ガスタービンにおけるバーナの燃料系統の部分域を洗浄する方法は本発明に基づいて以下の過程に従って行われる。即ち、燃料を燃料源からバーナに導入するための入口配管の用意、この入口配管に媒体をそれぞれ注入するためのバーナ近隣注入点およびバーナ遠隔注入点の用意、バーナ近隣注入点を介しての媒体の注入、入口配管におけるバーナ近隣注入点とバーナとの間に存在する燃料のバーナを介しての排出、バーナ遠隔注入点を介しての媒体の注入および入口配管におけるバーナ遠隔注入点とバーナ近隣注入点との間に存在する燃料のバーナ近隣注入点を介しての排出の過程に従って行われる。かかる方法は、特に両洗浄過程において燃料がバーナの方向に搬送されるので、入口配管の簡単で安価で且つ特に良好な浄化洗浄を可能にする。即ち、入口配管は燃料がその中を流れる方向と同じ方向に貫流洗浄される。これは実験で確認されているように、例えば入口配管における構造的に必然的に存在する突き当たりおよび結合箇所が良好に浄化されるという利点を有する。   A method of cleaning a partial region of a burner fuel system in a gas turbine is performed according to the present invention according to the following process. That is, preparation of an inlet pipe for introducing fuel from a fuel source to a burner, preparation of a burner adjacent injection point and a burner remote injection point for injecting a medium into the inlet pipe, and a medium via a burner adjacent injection point Injection, fuel discharge between the burner adjacent injection point and burner in the inlet pipe through the burner, medium injection through the burner remote injection point and burner remote injection point and burner adjacent injection in the inlet pipe This is done in accordance with the process of discharge through the burner adjacent injection point of fuel present between the points. Such a method allows for simple, inexpensive and particularly good cleaning of the inlet piping, especially since the fuel is transported in the direction of the burner in both cleaning processes. That is, the inlet pipe is washed through in the same direction as the direction in which the fuel flows. This has the advantage that, as confirmed by experiments, for example, the structurally inevitably abutting and joining points in the inlet pipe are well cleaned.

本発明に基づく方法の第１の有利な実施態様において、バーナ近隣注入点を介しての媒体の注入過程後に、バーナ遠隔注入点を介しての媒体の注入過程が実施される。この実施態様において、その過程が異なった順序で進行される場合よりも少ない量の燃料がバーナに運ばれる。   In a first advantageous embodiment of the method according to the invention, the medium injection process via the burner remote injection point is carried out after the medium injection process via the burner adjacent injection point. In this embodiment, less fuel is delivered to the burner than if the process proceeds in a different order.

本発明に基づく方法の第２の有利な実施態様において、入口配管におけるバーナ遠隔注入点とバーナ近隣注入点との間に存在する燃料がバーナ近隣注入点を介してドレン管に排出される。そのドレン管は排出された燃料の目的に適った除去および廃棄処理を可能にする。   In a second advantageous embodiment of the method according to the invention, the fuel present between the burner remote injection point and the burner neighboring injection point in the inlet pipe is discharged into the drain pipe via the burner neighboring injection point. The drain tube allows for a suitable removal and disposal of the discharged fuel.

本発明に基づく方法の第３の有利な実施態様において、媒体として水が利用される。水はガスタービンにおいて、ガスタービンの運転中に窒素酸化物の発生を少なくするために水をバーナに配量するＮＯｘ対策水供給装置に既に存在している。   In a third advantageous embodiment of the method according to the invention, water is used as the medium. Water is already present in gas turbines in NOx water supply systems that meter water into burners to reduce the generation of nitrogen oxides during operation of the gas turbine.

さらに本発明における課題は、燃料を燃料源からバーナに導入するための入口配管を備え、この入口配管にバーナ近隣注入点およびバーナ遠隔注入点がそれぞれ入口配管に媒体を注入するために設けられているガスタービンにおけるバーナの燃料系統によって解決される。   A further object of the present invention is to provide an inlet pipe for introducing fuel from a fuel source to a burner, and a burner vicinity injection point and a burner remote injection point are provided for injecting a medium into the inlet pipe, respectively. Solved by the burner fuel system in a gas turbine.

本発明に基づく燃料系統の第１の有利な実施態様において、第１注入管がバーナ近隣注入点に導かれ、第２注入管がバーナ遠隔注入点に導かれ、両注入管においてそれぞれその注入点の上流にその注入点への流量を調整するための調整機構が設けられている。この調整機構はバーナの通常運転中に燃料入口配管を異種媒体の注入に対して遮断する。   In a first advantageous embodiment of the fuel system according to the invention, the first injection pipe is led to the burner adjacent injection point, the second injection pipe is led to the burner remote injection point, and the injection points in both injection pipes respectively. An adjustment mechanism for adjusting the flow rate to the injection point is provided upstream. This adjustment mechanism shuts off the fuel inlet piping against the injection of different media during normal operation of the burner.

本発明に基づく燃料系統の第２の有利な実施態様において、バーナ近隣注入点とその上流に配置された調整機構との間において第１注入管から排出管（ドレン管）が分岐され、この排出管に調整機構が配置されている。その排出管は洗浄除去された燃料を的確に排出し、そのために第２過程中に前記調整機構で開けられる。   In a second advantageous embodiment of the fuel system according to the invention, a discharge pipe (drain pipe) is branched off from the first injection pipe between the injection point adjacent to the burner and the adjusting mechanism arranged upstream thereof. An adjustment mechanism is disposed on the tube. The discharge pipe accurately discharges the washed and removed fuel and is opened by the adjusting mechanism during the second process.

本発明に基づく燃料系統の第３の有利な実施態様において、入口配管においてバーナ遠隔注入点とバーナ近隣注入点との間に調整機構が設けられている。この調整機構は、第１過程中に燃料が燃料供給装置に押し戻されないようにするために、また本発明に基づいて特に回避する入口配管内における逆流が生じてしまわないようにするために、入口配管を閉鎖するために補助的に用いられる。   In a third advantageous embodiment of the fuel system according to the invention, an adjustment mechanism is provided in the inlet line between the burner remote injection point and the burner neighboring injection point. In order to prevent the fuel from being pushed back to the fuel supply device during the first process and to prevent back flow in the inlet pipe that is specifically avoided according to the present invention, Used auxiliary to close the inlet piping.

本発明に基づく燃料系統の第４の有利な実施態様において、前記複数の弁は多機能調整機構ないし多機能弁の形で単一の構造ユニットにまとめられている。かかる多機能調整機構はユニットとして作ることができ検査することもできる。これはまた燃料系統の内部において唯一の管路群だけで制御でき、即ち、全体として安価である。   In a fourth advantageous embodiment of the fuel system according to the invention, the plurality of valves are grouped into a single structural unit in the form of a multi-function regulator or multi-function valve. Such a multi-function adjusting mechanism can be made as a unit and can be inspected. This can also be controlled with only one group of lines inside the fuel system, i.e. it is inexpensive overall.

本発明に基づく燃料系統の第５の有利な実施態様において、入口配管においてバーナ近隣注入点とバーナとの間に１つの調整機構が設けられている。この調整機構は第２過程中における燃料の流出を確実に阻止する。   In a fifth advantageous embodiment of the fuel system according to the invention, an adjustment mechanism is provided in the inlet line between the burner adjacent injection point and the burner. This adjusting mechanism reliably prevents fuel from flowing out during the second process.

以下添付の概略図を参照して本発明に基づく解決策の実施例を詳細に説明する。   Embodiments of the solution according to the invention will now be described in detail with reference to the accompanying schematic drawings.

本発明に基づくガスタービンにおける燃料系統の原理図。The principle figure of the fuel system in the gas turbine based on this invention.

図１に本発明に基づく燃料系統が示され、この燃料系統において、（図示されてない）燃料源から燃料油の形の液体燃料が弁１０６、燃料油流れ分配器１０４および入口配管１００を介して（複数のうちの１つの）バーナ１０２に送られる。入口配管１００にバーナ近隣注入点１０８およびバーナ遠隔注入点１１０が形成されている。バーナ近隣注入点１０８に第１注入管１１２が通じ、この第１注入管１１２によって弁Ｖ２、水分配器１１４および調整弁１１６を介して水源としての（図示されてない）ＮＯｘ対策水供給装置から水が入口配管１００およびバーナ１０２に対して洗浄媒体として供給される。   FIG. 1 shows a fuel system according to the invention, in which liquid fuel in the form of fuel oil from a fuel source (not shown) passes through a valve 106, a fuel oil flow distributor 104 and an inlet pipe 100. To the burner 102 (one of the plurality). A burner vicinity injection point 108 and a burner remote injection point 110 are formed in the inlet pipe 100. A first injection pipe 112 leads to the burner vicinity injection point 108, and water is supplied from the NOx countermeasure water supply device (not shown) as a water source via the valve V 2, the water distributor 114 and the regulating valve 116 by the first injection pipe 112. Is supplied to the inlet pipe 100 and the burner 102 as a cleaning medium.

水分配器１１４から第２注入管１１８が第２注入点１１０に通じ、第２注入管１１８に弁Ｖ３が配置されている。また入口配管１００における第１注入点１０８と第２注入点１１０との間の管域に弁Ｖ４が配置されている。さらに第１注入管１１２から流れ方向において弁Ｖ２の下流でドレン管１２０が図示されてないドレン装置に通じ、ドレン管１２０に弁Ｖ１が配置されている。弁Ｖ１、Ｖ２、Ｖ３、Ｖ４は１つの多機能弁ＭＦＶの形で単一構造ユニットにまとめられている。   A second injection pipe 118 leads from the water distributor 114 to the second injection point 110, and a valve V <b> 3 is arranged in the second injection pipe 118. In addition, a valve V4 is disposed in a pipe region between the first injection point 108 and the second injection point 110 in the inlet pipe 100. Further, the drain pipe 120 communicates with a drain device (not shown) downstream of the valve V2 in the flow direction from the first injection pipe 112, and the valve V1 is arranged in the drain pipe 120. The valves V1, V2, V3, V4 are combined into a single structural unit in the form of one multi-function valve MFV.

入口配管１００における注入点１０８とバーナ１０２との間の管域に弁５の形の遮断機構が存在している。   A shut-off mechanism in the form of a valve 5 exists in a pipe area between the injection point 108 and the burner 102 in the inlet pipe 100.

ガスタービンのかかる燃料系統の配管、即ち、入口配管１００を洗浄するために、２回の過程で燃料油管の排液が行われる。まずバーナ１０２が媒体つまり水で洗浄される。そのためにＮＯｘ水供給装置から水が水管ないし注入管１１２およびバーナ近くのＴ形管部材（バーナ近隣注入点）１０８を介して燃焼器ないしバーナ１０２に圧送される（弁Ｖ２＝開、弁Ｖ１、Ｖ３、Ｖ４＝閉）。これによって、バーナ１０２およびＴ形管部材１０８とバーナ１０２との間の管部材（代表的には１ｍ（メートル）以下）から燃料油が排液される。   In order to clean the fuel system piping of the gas turbine, that is, the inlet piping 100, the fuel oil pipe is drained in two steps. First, the burner 102 is washed with a medium, that is, water. For this purpose, water is pumped from the NOx water supply device to the combustor or burner 102 via a water pipe or injection pipe 112 and a T-shaped pipe member (burner adjacent injection point) 108 near the burner (valve V2 = open, valve V1, V3, V4 = closed). As a result, the fuel oil is drained from the burner 102 and the tube member (typically 1 m (meter) or less) between the T-shaped tube member 108 and the burner 102.

第２過程において水が多機能弁ＭＦＶないしバーナ遠隔注入点１１０を介して燃料油・水注入ユニット（遮断機構１１６と水分配器１１４）から燃料油管ないし入口配管１００に導かれる（Ｖ２＝閉、Ｖ１、Ｖ３、Ｖ４＝開）。水が燃料油を前方にバーナ１０２に向けて押し出す。しかし燃料油はそこでバーナ１０２に噴射されず（これは望ましくない再燃作用を生じさせる）、Ｔ形管部材１０８を介して水管ないし注入管１１２に押し戻され、その場合、この時点においてバーナ入口管は（適当な弁装置としての）弁Ｖ５によって閉じられている。   In the second process, water is led from the fuel oil / water injection unit (the shutoff mechanism 116 and the water distributor 114) to the fuel oil pipe or the inlet pipe 100 via the multifunction valve MFV or the burner remote injection point 110 (V2 = closed, V1). V3, V4 = open). Water pushes the fuel oil forward toward the burner 102. However, the fuel oil is not injected there into the burner 102 (which causes an undesirable reburning action) and is pushed back through the T-tube member 108 to the water or injection tube 112, at which point the burner inlet tube is Closed by valve V5 (as a suitable valve device).

（燃料油・水注入ユニットにおける）燃料油供給装置の近くで燃料油が弁Ｖ１を介してドレン管１２０を通して排液装置ないしドレン装置に運ばれる。   In the vicinity of the fuel oil supply device (in the fuel oil / water injection unit), the fuel oil is conveyed to the drainage device or drain device through the drain pipe 120 via the valve V1.

本発明は通常の燃料油流れ方向において燃料油管ないし入口配管１００の完全な洗浄を可能にしている。   The present invention enables complete cleaning of the fuel oil pipe or inlet pipe 100 in the normal fuel oil flow direction.

他の利点は、低いか不足する燃焼器圧においても、並びに高速洗浄流による短い洗浄時間においても、燃料油管から燃料油を確実に除去できることにある。   Another advantage is that fuel oil can be reliably removed from the fuel oil tube at low or short combustor pressures, as well as at short cleaning times with high-speed cleaning streams.

１００：入口配管、１０２：バーナ、１０８：バーナ近隣注入点、１１０：バーナ遠隔注入点、１２０：ドレン管。   100: Inlet piping, 102: Burner, 108: Burner adjacent injection point, 110: Burner remote injection point, 120: Drain pipe.

Claims (10)

燃料を燃料源からバーナ（１０２）に導入するための入口配管（１００）の用意、該入口配管（１００）に媒体をそれぞれ注入するためのバーナ近隣注入点（１０８）およびバーナ遠隔注入点（１１０）の用意、バーナ近隣注入点（１０８）を介しての媒体の注入、入口配管（１００）におけるバーナ近隣注入点（１０８）とバーナ（１０２）との間に存在する燃料のバーナ（１０２）を介しての排出、バーナ遠隔注入点（１１０）を介しての媒体の注入および入口配管（１００）におけるバーナ遠隔注入点（１１０）とバーナ近隣注入点（１０８）との間に存在する燃料のバーナ近隣注入点（１０８）を介しての排出の過程を含むガスタービンにおけるバーナの燃料系統の部分域を洗浄する方法。   Preparation of an inlet pipe (100) for introducing fuel from a fuel source to the burner (102), a burner adjacent injection point (108) and a burner remote injection point (110) for injecting medium into the inlet pipe (100), respectively. ), Medium injection through burner proximity injection point (108), fuel burner (102) existing between burner proximity injection point (108) and burner (102) in inlet pipe (100) Via the burner, the injection of the medium via the burner remote injection point (110) and the burner of the fuel existing between the burner remote injection point (110) and the burner adjacent injection point (108) in the inlet pipe (100) A method for cleaning a sub-region of a burner fuel system in a gas turbine including a process of emissions through a neighboring injection point (108). バーナ近隣注入点（１０８）を介しての媒体の注入過程後に、バーナ遠隔注入点（１１０）を介しての媒体の注入過程が実施される請求項１に記載の方法。   The method according to claim 1, wherein the medium injection process via the burner remote injection point (110) is performed after the medium injection process via the burner proximity injection point (108). 入口配管（１００）におけるバーナ遠隔注入点（１１０）とバーナ近隣注入点（１０８）との間に存在する燃料が、バーナ近隣注入点（１０８）を介してドレン管（１２０）に排出される請求項１又は２に記載の方法。   The fuel present between the burner remote injection point (110) and the burner adjacent injection point (108) in the inlet pipe (100) is discharged to the drain pipe (120) via the burner adjacent injection point (108). Item 3. The method according to Item 1 or 2. 媒体として水が利用される請求項１ないし３のいずれか１つに記載の方法。   4. The method according to claim 1, wherein water is used as the medium. 燃料を燃料源からバーナ（１０２）に導入するための入口配管（１００）を備え、該入口配管（１００）にバーナ近隣注入点（１０８）およびバーナ遠隔注入点（１１０）がそれぞれ入口配管（１００）に媒体を注入するために設けられているガスタービンにおけるバーナ（１０２）の燃料系統。   An inlet pipe (100) for introducing fuel from a fuel source to the burner (102) is provided, and the inlet pipe (100) includes a burner neighboring injection point (108) and a burner remote injection point (110), respectively. The fuel system of the burner (102) in the gas turbine provided for injecting the medium into the medium. 第１注入管（１１２）がバーナ近隣注入点（１０８）に導かれ、第２注入管（１１８）がバーナ遠隔注入点（１１０）に導かれ、両注入管（１１２、１１８）においてそれぞれその注入点（１０８、１１０）の上流にその注入点への流量を調整するための調整機構（Ｖ２、Ｖ３）が設けられている請求項５に記載の燃料系統。   The first injection tube (112) is led to the burner adjacent injection point (108), the second injection tube (118) is led to the burner remote injection point (110), and the injection is made in both injection tubes (112, 118), respectively. 6. The fuel system according to claim 5, wherein an adjustment mechanism (V2, V3) for adjusting the flow rate to the injection point is provided upstream of the point (108, 110). バーナ近隣注入点（１０８）とその上流に配置された調整機構（Ｖ２）との間において第１注入管（１１２）から排出管（１２０）が分岐され、該排出管（１２０）に調整機構（Ｖ１）が配置されている請求項６に記載の燃料系統。   The discharge pipe (120) is branched from the first injection pipe (112) between the burner vicinity injection point (108) and the adjustment mechanism (V2) arranged upstream thereof, and the adjustment mechanism ( The fuel system according to claim 6, wherein V1) is arranged. 入口配管（１００）においてバーナ遠隔注入点（１１０）とバーナ近隣注入点（１０８）との間に調整機構（Ｖ４）が設けられている請求項５ないし７のいずれか１つに記載の燃料系統。   The fuel system according to any one of claims 5 to 7, wherein an adjustment mechanism (V4) is provided between the burner remote injection point (110) and the burner neighboring injection point (108) in the inlet pipe (100). . 前記複数の弁（Ｖ１、Ｖ２、Ｖ３、Ｖ４）が多機能調整機構の形で単一構造ユニットにまとめられている請求項６ないし８のいずれか１つに記載の燃料系統。   The fuel system according to any one of claims 6 to 8, wherein the plurality of valves (V1, V2, V3, V4) are grouped into a single structural unit in the form of a multi-function adjusting mechanism. 入口配管（１００）においてバーナ近隣注入点（１０８）とバーナ（１０２）との間に調整機構（Ｖ５）が設けられている請求項５ないし９のいずれか１つに記載の燃料系統。   The fuel system according to any one of claims 5 to 9, wherein an adjustment mechanism (V5) is provided between the burner adjacent injection point (108) and the burner (102) in the inlet pipe (100).
JP2011512910A 2008-06-09 2009-04-30 Method for cleaning a fuel system of a gas turbine and the fuel system Expired - Fee Related JP5220190B2 (en)

Applications Claiming Priority (3)

Application Number Priority Date Filing Date Title
DE102008027409.7 2008-06-09
DE102008027409 2008-06-09
PCT/EP2009/055266 WO2009149990A1 (en) 2008-06-09 2009-04-30 Method for rinsing a fuel system of a gas turbine and associated fuel system

Publications (2)

Publication Number Publication Date
JP2011522990A true JP2011522990A (en) 2011-08-04
JP5220190B2 JP5220190B2 (en) 2013-06-26

Family

ID=40940610

Family Applications (1)

Application Number Title Priority Date Filing Date
JP2011512910A Expired - Fee Related JP5220190B2 (en) 2008-06-09 2009-04-30 Method for cleaning a fuel system of a gas turbine and the fuel system

Country Status (7)

Country Link
US (1) US9175606B2 (en)
EP (1) EP2304205B1 (en)
JP (1) JP5220190B2 (en)
CN (1) CN102057145B (en)
RU (1) RU2460894C1 (en)
TW (1) TWI496987B (en)
WO (1) WO2009149990A1 (en)

Cited By (3)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
JP2013060843A (en) * 2011-09-13 2013-04-04 Hitachi Ltd Gas turbine fuel system, and method for cleaning the same
JP2017500478A (en) * 2013-12-09 2017-01-05 シーメンス アクティエンゲゼルシャフト Gas turbine with bypass conduit for improved fuel conduit cleaning
JP2018520290A (en) * 2015-04-28 2018-07-26 シーメンス アクティエンゲゼルシャフト Injection liquid fuel nozzle and supply pipe using flow dividing device

Families Citing this family (14)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US8430112B2 (en) * 2010-07-13 2013-04-30 Siemens Industry, Inc. Slurry feed system and method
WO2013147632A1 (en) * 2012-03-29 2013-10-03 General Electric Company Bi-directional end cover with extraction capability for gas turbine combustor
US8893923B2 (en) * 2012-11-28 2014-11-25 Intermolecular, Inc. Methods and systems for dispensing different liquids for high productivity combinatorial processing
US9371995B2 (en) * 2013-04-11 2016-06-21 General Electric Company Pulsed water flush of liquid fuel valves and combustion nozzles
US10012148B2 (en) * 2014-05-23 2018-07-03 General Electric Company Method of purging a combustor
FR3028245B1 (en) * 2014-11-06 2019-05-24 Airbus Operations FUEL SUPPLY CIRCUIT OF AN AIRCRAFT
EP3101238A1 (en) * 2015-06-05 2016-12-07 Siemens Aktiengesellschaft Fuel line system with flow splitter and by-pass line
US9989257B2 (en) * 2015-06-24 2018-06-05 Delavan Inc Cooling in staged fuel systems
JP6965167B2 (en) * 2018-01-12 2021-11-10 三菱パワー株式会社 Gas turbine cogeneration system and its operation switching method
US11156162B2 (en) * 2018-05-23 2021-10-26 General Electric Company Fluid manifold damper for gas turbine engine
US11506125B2 (en) 2018-08-01 2022-11-22 General Electric Company Fluid manifold assembly for gas turbine engine
US11261797B2 (en) 2018-11-05 2022-03-01 General Electric Company System and method for cleaning, restoring, and protecting gas turbine engine components
FR3089254B1 (en) 2018-11-30 2021-11-12 Ge Energy Products France Snc DRAINAGE CIRCUIT OF A COMBUSTION CHAMBER AND PROCESS FOR DETERMINING THE FAILURE OF SUCH A CIRCUIT
US11555413B2 (en) 2020-09-22 2023-01-17 General Electric Company System and method for treating an installed and assembled gas turbine engine

Citations (7)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
JPH0367029A (en) * 1989-07-28 1991-03-22 United Technol Corp <Utc> Fuel control apparatus utilizing multi- function valve
JPH11210494A (en) * 1998-01-26 1999-08-03 Toshiba Corp Purge device for fuel supply device of gas turbine and method for operating purge device
JPH11324720A (en) * 1998-05-08 1999-11-26 Mitsubishi Heavy Ind Ltd Gas turbine fuel oil purge system
JP2000064855A (en) * 1998-02-26 2000-02-29 Abb Res Ltd Method for positively eliminating liquid fuel from fuel system of gas turbine and device for executing this method
JP2002021649A (en) * 2000-07-06 2002-01-23 Futaba Industrial Co Ltd Evaporative emission system module
JP2002129981A (en) * 2000-10-30 2002-05-09 Toshiba Corp Fuel supply system in gas turbine
JP2007155170A (en) * 2005-12-02 2007-06-21 Hitachi Ltd Fuel nozzle, gas turbine combustor, fuel nozzle of gas turbine combustor, and remodeling method of gas turbine combustor

Family Cites Families (23)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US4041695A (en) * 1975-11-21 1977-08-16 The Garrett Corporation Fuel system pneumatic purge apparatus and method
US4984424A (en) * 1988-02-16 1991-01-15 Sundstrand Corporation Fuel injection system for a turbine engine
RU1815404C (en) 1990-08-09 1993-05-15 Курганский сельскохозяйственный институт Method and apparatus for cleaning sprayers of diesel nozzles
GB9025778D0 (en) * 1990-11-27 1991-01-09 Rolls Royce Plc Improvements in or relating to gas generators
US5784875A (en) * 1995-11-27 1998-07-28 Innovative Control Systems, Inc. Water injection into a gas turbine using purge air
US6092362A (en) * 1996-11-27 2000-07-25 Hitachi, Ltd. Gas-turbine combustor with load-responsive premix burners
EP0952317A3 (en) * 1998-04-21 2002-04-17 Mitsubishi Heavy Industries, Ltd. Purging system for a gas turbine fuel supply
CA2270672C (en) * 1998-05-08 2002-03-05 Yukimasa Nakamoto Gas turbine fuel system comprising fuel oil distribution control system, fuel oil purge system, purging air supply system, and fuel nozzle wash system
DE59806050D1 (en) 1998-05-25 2002-11-28 Alstom Arrangement for the optional introduction of fuel and / or water into a combustion chamber
AUPP627098A0 (en) 1998-09-30 1998-10-22 Orbital Engine Company (Australia) Proprietary Limited Purge fuel flow rate determination method
JP3381250B2 (en) 1998-11-16 2003-02-24 栗田工業株式会社 Gas dissolving cleaning water flow pipe
US6367239B1 (en) * 1998-12-09 2002-04-09 General Electric Company Fuel delivery systems and method
JP4335397B2 (en) * 2000-02-01 2009-09-30 三菱重工業株式会社 Gas turbine fuel gas dredge equipment
EP1277920A1 (en) * 2001-07-19 2003-01-22 Siemens Aktiengesellschaft Procedure for operating a combuster of a gas-turbine and power plant
US6959535B2 (en) 2003-01-31 2005-11-01 General Electric Company Differential pressure induced purging fuel injectors
US6898926B2 (en) 2003-01-31 2005-05-31 General Electric Company Cooled purging fuel injectors
US6932093B2 (en) 2003-02-24 2005-08-23 General Electric Company Methods and apparatus for washing gas turbine engine combustors
US7104070B2 (en) * 2004-03-04 2006-09-12 General Electric Company Liquid fuel nozzle apparatus with passive water injection purge
US7721521B2 (en) * 2005-11-07 2010-05-25 General Electric Company Methods and apparatus for a combustion turbine fuel recirculation system and nitrogen purge system
US20070289208A1 (en) * 2006-06-07 2007-12-20 Yos Soetanto Theosabrata Landscaping vegetation border unit
US7954310B2 (en) * 2006-06-16 2011-06-07 Siemens Energy, Inc. Fuel oil bi-directional flow divider
US8127524B2 (en) * 2007-01-10 2012-03-06 Hamilton Sundstrand Corporation Gas turbine fuel metering unit
US7921651B2 (en) * 2008-05-05 2011-04-12 General Electric Company Operation of dual gas turbine fuel system

Patent Citations (7)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
JPH0367029A (en) * 1989-07-28 1991-03-22 United Technol Corp <Utc> Fuel control apparatus utilizing multi- function valve
JPH11210494A (en) * 1998-01-26 1999-08-03 Toshiba Corp Purge device for fuel supply device of gas turbine and method for operating purge device
JP2000064855A (en) * 1998-02-26 2000-02-29 Abb Res Ltd Method for positively eliminating liquid fuel from fuel system of gas turbine and device for executing this method
JPH11324720A (en) * 1998-05-08 1999-11-26 Mitsubishi Heavy Ind Ltd Gas turbine fuel oil purge system
JP2002021649A (en) * 2000-07-06 2002-01-23 Futaba Industrial Co Ltd Evaporative emission system module
JP2002129981A (en) * 2000-10-30 2002-05-09 Toshiba Corp Fuel supply system in gas turbine
JP2007155170A (en) * 2005-12-02 2007-06-21 Hitachi Ltd Fuel nozzle, gas turbine combustor, fuel nozzle of gas turbine combustor, and remodeling method of gas turbine combustor

Cited By (4)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
JP2013060843A (en) * 2011-09-13 2013-04-04 Hitachi Ltd Gas turbine fuel system, and method for cleaning the same
JP2017500478A (en) * 2013-12-09 2017-01-05 シーメンス アクティエンゲゼルシャフト Gas turbine with bypass conduit for improved fuel conduit cleaning
US10184351B2 (en) 2013-12-09 2019-01-22 Siemens Aktiengesellschaft Gas turbine with a bypass line for improved fuel line flushing, and method for flushing a gas turbine
JP2018520290A (en) * 2015-04-28 2018-07-26 シーメンス アクティエンゲゼルシャフト Injection liquid fuel nozzle and supply pipe using flow dividing device

Also Published As

Publication number Publication date
US9175606B2 (en) 2015-11-03
JP5220190B2 (en) 2013-06-26
RU2010154443A (en) 2012-07-20
CN102057145A (en) 2011-05-11
EP2304205A1 (en) 2011-04-06
EP2304205B1 (en) 2013-08-14
US20110146807A1 (en) 2011-06-23
TWI496987B (en) 2015-08-21
TW201007007A (en) 2010-02-16
CN102057145B (en) 2014-08-20
WO2009149990A1 (en) 2009-12-17
RU2460894C1 (en) 2012-09-10

Similar Documents

Publication Publication Date Title
JP5220190B2 (en) Method for cleaning a fuel system of a gas turbine and the fuel system
JP4253389B2 (en) Method for reliably removing liquid fuel from a fuel system of a gas turbine and apparatus for carrying out the method
US9188061B2 (en) System for turbine combustor fuel assembly
JP5465256B2 (en) Method for cleaning an area of a gas turbine fuel system
JP2002161757A (en) Reducing method of burner emission and its equipment
CN103104345A (en) System for purging gas fuel circuit for a gas turbine engine
JP2011231762A (en) ALTERNATE METHOD FOR DILUENT INJECTION FOR GAS TURBINE NOx EMISSION CONTROL
JP6224249B2 (en) Gas turbine with bypass conduit for improved fuel conduit cleaning
EP3147484B1 (en) Method and system for reliable gas to liquid transfer
CN106168383A (en) Gas-turbine unit liquid fuel feed system and method
CN101576008A (en) Single manifold dual gas turbine fuel system
JP2016191527A (en) Chemical cleaning method for main steam pipe or reheat steam pipe
CN201739627U (en) Dredging and anti-sticking device for gas pipe valve
JP3555235B2 (en) Fuel purge method for pressurized fluidized bed boiler
CN206924711U (en) Blender back purge system
JP5632786B2 (en) Waste heat recovery boiler
JPH11324722A (en) System for cleaning gas turbine fuel nozzle
RU2317451C1 (en) Jet pump starting system
JP2018071545A (en) System and method for purging fuel from turbomachine
RU2064151C1 (en) Method for cleaning and passivating working medium path of once-through boiler
KR100337160B1 (en) Burner attaching device
KR20130070621A (en) An apparatus for reducing nitrogen dioxide from exhaust gas by double injection and the method using the same
RU2052634C1 (en) Device for cleaning oil system of turbo-machine
KR200183763Y1 (en) Sootblower Condenate Water Drain equipment
CN116182147A (en) Deoxygenated water supply method and deoxygenated water supply system

Legal Events

Date Code Title Description
A529 Written submission of copy of amendment under article 34 pct

Free format text: JAPANESE INTERMEDIATE CODE: A529

Effective date: 20110208

A621 Written request for application examination

Free format text: JAPANESE INTERMEDIATE CODE: A621

Effective date: 20110606

A977 Report on retrieval

Free format text: JAPANESE INTERMEDIATE CODE: A971007

Effective date: 20120425

A131 Notification of reasons for refusal

Free format text: JAPANESE INTERMEDIATE CODE: A131

Effective date: 20120501

A521 Request for written amendment filed

Free format text: JAPANESE INTERMEDIATE CODE: A523

Effective date: 20120801

TRDD Decision of grant or rejection written
A01 Written decision to grant a patent or to grant a registration (utility model)

Free format text: JAPANESE INTERMEDIATE CODE: A01

Effective date: 20130205

A61 First payment of annual fees (during grant procedure)

Free format text: JAPANESE INTERMEDIATE CODE: A61

Effective date: 20130305

FPAY Renewal fee payment (event date is renewal date of database)

Free format text: PAYMENT UNTIL: 20160315

Year of fee payment: 3

R150 Certificate of patent or registration of utility model

Ref document number: 5220190

Country of ref document: JP

Free format text: JAPANESE INTERMEDIATE CODE: R150

Free format text: JAPANESE INTERMEDIATE CODE: R150

R250 Receipt of annual fees

Free format text: JAPANESE INTERMEDIATE CODE: R250

R250 Receipt of annual fees

Free format text: JAPANESE INTERMEDIATE CODE: R250

R250 Receipt of annual fees

Free format text: JAPANESE INTERMEDIATE CODE: R250

R250 Receipt of annual fees

Free format text: JAPANESE INTERMEDIATE CODE: R250

R250 Receipt of annual fees

Free format text: JAPANESE INTERMEDIATE CODE: R250

R250 Receipt of annual fees

Free format text: JAPANESE INTERMEDIATE CODE: R250

LAPS Cancellation because of no payment of annual fees